Aircraft fuselage

Aeronautics and astronautics – Aircraft structure – Fuselage and body construction

Patent

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Details

244 87, B64C 100

Patent

active

049019503

ABSTRACT:
A single aft located prop aircraft having an X-axis in alignment with the line of thrust of the aircraft; a Y-axis transverse to the X-axis, the Y-axis being in parallel with the length of a single main wing; and a Z-axis transverse to the plane defined by the X and Y-axes. The fuselage exhibits Y-axis symmetry about the thrust line and, in addition, substantial X-axis symmetry about a line defined by the forward edge of the main wing. The fuselage assembly includes a substantially conical cone, the cone having its root at the beginning of the pilot's cabin, and the cone subtending a vertex in the range of 15 to 20 degrees. The fuselage nose possesses an X-axis length to Z axis base diameter ratio in the range of 2 to 3. The aircraft further includes a single main wing secured on top of the upper fuselage in which the XY plane of the wing is in alignment with the line of thrust of the aft-located prop. The aircraft also includes a tail fin system itself having three separate tailfins, one of the fins directed downwardly in the negative Z direction and perpendicularly to the plane of the fixed wing. The second and third tail fins of the tail fin system are disposed respectively symmetrically about the XZ plane of the aircraft, each of those fins disposed at an angle, relative to the plane of the fixed wing, in the range of 30 to 60 degrees.

REFERENCES:
patent: D150434 (1948-08-01), Lovejoy et al.
patent: 2424889 (1947-07-01), Holmes
patent: 3188025 (1965-06-01), Moorehead
patent: 3191888 (1965-06-01), Sklenka
patent: 3455523 (1969-07-01), Hertel

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